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FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX74_CL5_140 (fx74cl5140-il)
Reynolds number: 200,000
Max Cl/Cd: 73.76 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74cl5140-il-200000-n5.txt
Download as CSV file: xf-fx74cl5140-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX74_CL5_140                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.2827   0.09895   0.09253  -0.1336   0.5427   0.0164
  -9.500   0.2916   0.09683   0.09041  -0.1345   0.5404   0.0168
  -9.250   0.3005   0.09480   0.08838  -0.1353   0.5379   0.0169
  -9.000   0.3085   0.09287   0.08646  -0.1364   0.5360   0.0171
  -8.750   0.3165   0.09101   0.08458  -0.1372   0.5338   0.0172
  -8.500   0.3232   0.08926   0.08282  -0.1383   0.5323   0.0173
  -8.250   0.3334   0.08684   0.08038  -0.1386   0.5305   0.0174
  -8.000   0.3441   0.08457   0.07810  -0.1387   0.5285   0.0178
  -7.750   0.3534   0.08262   0.07618  -0.1392   0.5266   0.0180
  -7.500   0.3624   0.08074   0.07431  -0.1396   0.5247   0.0182
  -7.250   0.3711   0.07883   0.07242  -0.1401   0.5230   0.0189
  -7.000   0.3794   0.07699   0.07060  -0.1405   0.5214   0.0192
  -6.750   0.3866   0.07514   0.06877  -0.1409   0.5199   0.0201
  -6.500   0.3923   0.07350   0.06715  -0.1414   0.5185   0.0205
  -6.250   0.3902   0.07242   0.06611  -0.1418   0.5173   0.0208
  -6.000   0.4043   0.06986   0.06353  -0.1410   0.5158   0.0215
  -5.750   0.4106   0.06837   0.06204  -0.1406   0.5145   0.0222
  -5.500   0.4189   0.06675   0.06042  -0.1411   0.5133   0.0232
  -5.250   0.4284   0.06499   0.05867  -0.1423   0.5121   0.0240
  -5.000   0.4404   0.06305   0.05678  -0.1458   0.5108   0.0248
  -4.750   0.4596   0.06067   0.05441  -0.1522   0.5094   0.0250
  -4.500   0.4726   0.05837   0.05214  -0.1526   0.5078   0.0253
  -4.250   0.4847   0.05651   0.05030  -0.1519   0.5062   0.0259
  -4.000   0.5026   0.05447   0.04825  -0.1541   0.5046   0.0267
  -3.750   0.5256   0.05215   0.04591  -0.1582   0.5030   0.0278
  -3.500   0.5809   0.04794   0.04152  -0.1737   0.5015   0.0299
  -3.250   0.6026   0.04545   0.03900  -0.1758   0.5002   0.0305
  -3.000   0.6246   0.04368   0.03720  -0.1772   0.4989   0.0316
  -2.750   0.6991   0.03964   0.03269  -0.1929   0.4975   0.0360
  -2.500   0.7172   0.03769   0.03079  -0.1932   0.4963   0.0370
  -2.250   0.7492   0.03596   0.02902  -0.1964   0.4951   0.0395
  -2.000   0.8010   0.03315   0.02595  -0.2041   0.4936   0.0448
  -1.500   0.8813   0.02972   0.02221  -0.2125   0.4907   0.0557
  -1.250   0.9264   0.02812   0.02033  -0.2172   0.4892   0.0651
  -1.000   0.9806   0.02537   0.01707  -0.2226   0.4877   0.0454
  -0.500   1.0693   0.02206   0.01281  -0.2288   0.4848   0.0237
  -0.250   1.1039   0.02144   0.01195  -0.2302   0.4833   0.0224
   0.000   1.1370   0.02105   0.01130  -0.2312   0.4820   0.0213
   0.250   1.1686   0.02088   0.01097  -0.2321   0.4808   0.0208
   0.500   1.2012   0.02068   0.01070  -0.2333   0.4796   0.0205
   0.750   1.2318   0.02053   0.01060  -0.2341   0.4784   0.0204
   1.000   1.2626   0.02048   0.01057  -0.2350   0.4770   0.0204
   1.250   1.2934   0.02050   0.01060  -0.2359   0.4756   0.0205
   1.500   1.3233   0.02058   0.01065  -0.2367   0.4740   0.0208
   1.750   1.3530   0.02067   0.01071  -0.2373   0.4723   0.0215
   2.000   1.3821   0.02078   0.01078  -0.2379   0.4706   0.0250
   2.500   1.4542   0.02042   0.01168  -0.2423   0.4674   0.7315
   2.750   1.4790   0.02060   0.01187  -0.2418   0.4661   0.7787
   3.000   1.5018   0.02073   0.01202  -0.2408   0.4649   0.8251
   3.250   1.5183   0.02074   0.01209  -0.2385   0.4638   0.8891
   3.500   1.5370   0.02088   0.01232  -0.2369   0.4623   1.0000
   3.750   1.5630   0.02124   0.01269  -0.2370   0.4606   1.0000
   4.000   1.5891   0.02161   0.01306  -0.2371   0.4590   1.0000
   4.250   1.6152   0.02197   0.01342  -0.2372   0.4575   1.0000
   4.500   1.6411   0.02234   0.01378  -0.2373   0.4560   1.0000
   4.750   1.6670   0.02269   0.01415  -0.2374   0.4546   1.0000
   5.000   1.6929   0.02304   0.01449  -0.2375   0.4532   1.0000
   5.250   1.7189   0.02338   0.01482  -0.2376   0.4519   1.0000
   5.500   1.7450   0.02371   0.01513  -0.2377   0.4507   1.0000
   5.750   1.7714   0.02403   0.01545  -0.2379   0.4495   1.0000
   6.000   1.7983   0.02438   0.01576  -0.2382   0.4482   1.0000
   6.250   1.8201   0.02487   0.01634  -0.2376   0.4466   1.0000
   6.500   1.8400   0.02541   0.01700  -0.2367   0.4448   1.0000
   6.750   1.8604   0.02595   0.01766  -0.2360   0.4431   1.0000
   7.000   1.8811   0.02647   0.01827  -0.2352   0.4414   1.0000
   7.250   1.9020   0.02697   0.01885  -0.2346   0.4398   1.0000
   7.500   1.9232   0.02741   0.01935  -0.2339   0.4380   1.0000
   7.750   1.9452   0.02777   0.01977  -0.2334   0.4363   1.0000
   8.000   1.9683   0.02807   0.02010  -0.2330   0.4346   1.0000
   8.250   1.9925   0.02836   0.02041  -0.2329   0.4331   1.0000
   8.500   2.0160   0.02876   0.02084  -0.2327   0.4317   1.0000
   8.750   2.0225   0.02969   0.02199  -0.2297   0.4293   1.0000
   9.000   2.0300   0.03055   0.02305  -0.2269   0.4270   1.0000
   9.250   2.0377   0.03137   0.02401  -0.2241   0.4250   1.0000
   9.500   2.0474   0.03214   0.02490  -0.2217   0.4231   1.0000
   9.750   2.0595   0.03285   0.02570  -0.2198   0.4214   1.0000
  10.000   2.0741   0.03346   0.02641  -0.2183   0.4198   1.0000
  10.250   2.0914   0.03399   0.02702  -0.2172   0.4184   1.0000
  10.500   2.1115   0.03445   0.02754  -0.2166   0.4172   1.0000
  10.750   2.0999   0.03639   0.02971  -0.2117   0.4146   1.0000
  11.000   2.0777   0.03915   0.03272  -0.2062   0.4113   1.0000
  11.250   2.0691   0.04137   0.03511  -0.2027   0.4083   1.0000
  11.500   2.0735   0.04285   0.03670  -0.2008   0.4061   1.0000
  11.750   2.0865   0.04377   0.03771  -0.1998   0.4043   1.0000
  12.000   2.1109   0.04376   0.03775  -0.1997   0.4026   1.0000
  12.250   1.9613   0.06062   0.05505  -0.1903   0.3923   1.0000
  12.500   1.9773   0.06151   0.05602  -0.1899   0.3906   1.0000
  12.750   2.0120   0.06010   0.05466  -0.1900   0.3894   1.0000
  13.000   1.8705   0.08175   0.07652  -0.1879   0.3732   1.0000
  13.250   1.9161   0.07837   0.07320  -0.1876   0.3739   1.0000
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